joint strike fighter f-35c - virginia techmason/mason_f/jsfs05.pdff-35c overview first flight:...
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F-35 Purpose• The JSF is a fighter platform with a variant design for
all branches of the military.• 3 production versions are planned:
1) F-35A: CTOL variant to replace F-16 & A-102) F-35B: STOVL variant to replace AV-8B, F/A-18 C/D, Sea
Harrier, and GR-7. Will complement F-223) F-35C: CV variant. Our analysis will focus on this version of
the JSF
• The F-35C model was designed with larger wings andtail control surfaces for carrier operations
• It is also strengthened structurally to handle catapultlaunches and arrested landings
Information courtesy of www.jsf.mil
F-35C Mission Roles
• The F-35C is the carrier based variant of the JSF,designed and built for STOL capability.
• It is a multi-role, stealthy, survivable fighter designed tocomplement the F/A-18 E/F.
• AI: Medium level attacks using precision guided, freefallor retarded bombs
• CAS: Air action against hostile targets, in closeproximity to friendly forces
• Fleet defense: Aerial patrolling of ships
F-35C OverviewFirst flight: 02/12/2001
Crew: 1
Data for F-35C available “Jane’s All the World’s Aircraft 2004-2005”Picture available www.jsf.mil
Mach 1.8Max speed at altitude
20,000+Payload (lbs)
66,850MTOGW (lbs)
30,618Wempty (lbs)
620.00Reference Area (ft2)
15.25Tailscrape angle (deg)
28.3Tailspan (ft)
15.5Height (ft)
51.4Length (ft)
29.8Folded span (ft)
43.0Wingspan (ft)
Propulsion• Pratt & Whitney F135
• Thrust = 40,000 lbs
• T/Wmax = 0.598
• TSFC was unavailable
F-35B STOVL lifting fan
PW F135
Pictures courtesy of www.pratt-whitney.com and www.rollsroyce.com
Weights
F-35B STOVL variant on display at NASM Dulles Airport
0.29Wfuel/TOGW
0.3Wpayload/TOGW
107.82W/Smax (lb/ft2)
66,850MTOGW (lbs)
19,624Wfuel (lbs)
20,000+Max Payload(lbs)
30,618Wempty (lbs)
VLMpc vs. AVL
AVL available from http://raphael.mit.edu/avl/ VLMpc available from http://www.aoe.vt.edu/~mason/Mason_f/MRsoft.html
0.07070
0.06214
CL_
(per degree)
-12.99
-10.30
Static Margin(% mac)
-12.9929.6916.9331.44AVL
-10.3029.2416.9331.44VLMpc
Static Margin(% mac)
Neutral Point(ft. from nose)
MAC(ft)
Center ofGravity
(ft. from nose)
Method ofAnalysis
CG Estimate done using landing gear locations and Kirschbaum’s suggestions
Spanload Distributions• Obtained from VLMpc
• Load split:67% wing-body 33% tail
-1 -0.9 -0.8 -0.7 -0.6 -0.5 -0.4 -0.3 -0.2 -0.1 00
0.05
0.1
0.15
0.2
0.25
0.3
0.35Spanload distribution at CL = 0.323
2y/b
Spanload data
-1 -0.9 -0.8 -0.7 -0.6 -0.5 -0.4 -0.3 -0.2 -0.1 00
0.2
0.4
0.6
0.8
1
1.2
1.4Spanload Coefficient distribution
2y/b
Spanload data
Flat Wing Spanload coefficient Flat wing Spanload at cruise
CL Distribution
-1 -0.9 -0.8 -0.7 -0.6 -0.5 -0.4 -0.3 -0.2 -0.1 0
0.8
1
1.2
1.4
1.6
1.8
2
2y/b
Cl/CL
Cl/CL versus 2y/b
FRICTION Analysis
0.324CL cruise
14.47L/Dmax
0.0119cD0
0.6M
30,000 ftAltitude
• Wetted area is estimated of the figure of the airplane• Swet = 2589.63 ft2
0.2 0.3 0.4 0.5 0.6 0.7 0.80.01
0.0105
0.011
0.0115
0.012
0.0125
0.013
0.0135
0.014
0.0145
0.015
Mach number
Cd0
Plot of Cd0 vs Mach number
h = 30K fth = 35K fth = 40K ft
References
• http://www.deagel.com
• http://www.raf.mod.uk
• http://www.airforce-technology.com/projects/jsf/specs.html
• www.jsf.mil
• Jane’s All The World’s Aircraft: 2004-2005
Relevant Equations• (L/D)max = 14.47 (FRICTION)
• Rangemax = 1480 km– TSFC Data unavailable from Pratt
• CL Cruise = 0.324
• CL max = 3 – 3.5?– Raymer1 suggests that STOL
aircraft such as carrier-based
fighters require a max lift
coefficient upwards of 3.0. It is
our estimation that with the F-35C’s
high lift devices it could achieve
slightly more.
1 – Raymer, Daniel. “Aircraft Design: A Conceptual Approach”, 3rd Edition
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